CN109723559A - Gas-turbine unit including two speed separate compressor - Google Patents
Gas-turbine unit including two speed separate compressor Download PDFInfo
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- CN109723559A CN109723559A CN201811255881.6A CN201811255881A CN109723559A CN 109723559 A CN109723559 A CN 109723559A CN 201811255881 A CN201811255881 A CN 201811255881A CN 109723559 A CN109723559 A CN 109723559A
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- Prior art keywords
- compressor
- turbine
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- box
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
- F05D2220/3219—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for the last stage of a compressor or a high pressure compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/40—Transmission of power
- F05D2260/403—Transmission of power through the shape of the drive components
- F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Gas-turbine unit includes low pressure compressor, high pressure compressor, turbine and gear-box.High pressure compressor includes the multiple grades for being divided into front part and rear portion.One or two of front part and rear portion of high pressure compressor are driven by turbine by gear-box, and front part and rear portion are rotated at different rates.
Description
Technical field
Disclosure theme relates generally to gas-turbine unit.More specifically, this theme is related to gas-turbine unit,
It includes the gear-box for the speed for adjusting the selected grade of separate compressor.
Background technique
Gas-turbine unit generally includes the fan for being arranged to flow communication with one another and core.In addition, gas turbine
The core of engine is generally comprised in the compressor section of crossfire order, combustion sec-tion, turbine section and exhaust section.It is operating
In, air provides the entrance to compressor section from fan, and in the compressor section, one or more axial compressors are progressive
Ground compressed air, until air reaches burning block.Fuel is mixed with compressed air and is burnt in burning block to mention
For burning gases.Burning gases are transmitted to turbine from burning block.Turbine is driven by the burning gases stream of turbine
Section, and exhaust section is then transmitted through for example to atmosphere.
The compressor section and turbine of traditional gas turbine engine pass through one or more axis or spool connection.More
Specifically, low pressure compressor and low-pressure turbine can be coupled by low pressure spool, and high pressure compressor and high-pressure turbine can pass through
High pressure spool connection.It should be noted, however, that the revolving speed of the rear class of compound compressor is usually by before with relatively large radius
The limitation of the tip speed constraint of grade.It can be improved the tip speed of rear class by simply increasing its radius, but relative to
Tip clearance, blade height may become unacceptably small, and which increase the losses to deciding grade and level.
Therefore, the gas-turbine unit with improved compressor section will be useful.More specifically, have for
Reduced compressor size and improved performance and efficiency will be with the multistage two speed separate compressor that friction speed rotates
Particularly advantageous.
Summary of the invention
Each aspect of the present invention and advantage will illustrate partly in the following description, or can from the description it is clear that
Or can implementation through the invention and learn.
In an exemplary embodiment of the disclosure, gas-turbine unit includes the turbine comprising turbine and position
Compressor section in the upstream of turbine, compressor section include compressor, and compressor includes front part and posterior
Point.Gas-turbine unit further includes gear-box, and at least one of front part and rear portion of compressor are led to by turbine
Cross gear-box driving.
In another exemplary embodiment of the present disclosure, gas-turbine unit includes the turbine comprising turbine and position
Upstream in turbine and compressor section including low pressure compressor and high pressure compressor, high pressure compressor includes front
Part and rear portion.Gas-turbine unit further includes gear-box, in the front part and rear portion of high pressure compressor
At least one is driven by turbine by gear-box.
A kind of gas-turbine unit of technical solution 1. comprising:
Turbine, the turbine include turbine；
Compressor section, the compressor section is positioned at the upstream of the turbine and including compressor, described
Compressor includes front part and rear portion；And
Gear-box, at least one of front part and rear portion of the compressor pass through the tooth by the turbine
Roller box driving.
The gas-turbine unit according to technical solution 1 of technical solution 2., wherein the front of the compressor
Part includes the first multi-stage compression rotor blade, and the first multi-stage compression rotor blade limits between the first average axial direction
Away from, and wherein, the rear portion of the compressor includes the second multi-stage compression rotor blade, second compound compressor
Rotor blade limits the second average axial spacing, and wherein, and the described second average axial spacing is less than or equal to described first
Twice of average axial spacing.
The gas-turbine unit according to technical solution 2 of technical solution 3., wherein the described second average axial spacing
Less than or equal to the described first average axial spacing.
The gas-turbine unit according to technical solution 1 of technical solution 4., wherein the front of the compressor
Part is driven by the turbine by the gear-box, so that the front part of the compressor is configured to than the compression
The rear portion of machine more slowly rotates.
The gas-turbine unit according to technical solution 1 of technical solution 5., wherein the front of the compressor
Part and the rear portion are driven by the turbine by the gear-box.
The gas-turbine unit according to technical solution 1 of technical solution 6., wherein the compressor is high pressure compressed
Machine, wherein the compressor section further includes low pressure compressor.
The gas-turbine unit according to technical solution 6 of technical solution 7., wherein the turbine is high-pressure turbine,
And wherein the turbine further includes low-pressure turbine.
The gas-turbine unit according to technical solution 1 of technical solution 8., wherein the gear-box is planetary gear
Case.
The gas-turbine unit according to technical solution 1 of technical solution 9., wherein the compressor section further includes
Compressor discharge nozzle module, wherein the gear-box is installed to the compressor discharge nozzle module.
The gas-turbine unit according to technical solution 1 of technical solution 10., wherein the gear-box is located at described
The front of the compressor of compressor section.
The gas-turbine unit according to technical solution 1 of technical solution 11., wherein the gear-box is along described
The axial direction of gas-turbine unit is aligned with the rear portion of the front part of the compressor or the compressor.
The gas-turbine unit according to technical solution 1 of technical solution 12., wherein the compressor it is described before
Portion part is configured to rotate on the first circumferencial direction of the gas-turbine unit, wherein the compressor it is described after
Portion part is configured to rotate on the second circumferencial direction of the gas-turbine unit, and wherein, the gas turbine hair
First circumferencial direction of motivation and the second circumferencial direction of the gas-turbine unit are opposite.
The gas-turbine unit according to technical solution 1 of technical solution 13., wherein the compressor it is described before
Portion part is configured to rotate on the first circumferencial direction of the gas-turbine unit, and wherein, the institute of the compressor
Rear portion is stated also to be configured to rotate on the first circumferencial direction of the gas-turbine unit.
The gas-turbine unit according to technical solution 1 of technical solution 14., further include:
Burning block, wherein the compressor section, the burning block and the turbine press crossfire sequence cloth
It sets.
The gas-turbine unit according to technical solution 14 of technical solution 15., wherein the compressor section includes
Centrifugal compressor.
The gas-turbine unit according to technical solution 1 of technical solution 16., further include:
Fan, wherein the fan is at least partly driven by the turbine by the gear-box.
The gas-turbine unit according to technical solution 1 of technical solution 17., wherein the compressor is high pressure pressure
Contracting machine, wherein the compressor section further includes low pressure compressor, and wherein, the low pressure compressor is led to by the turbine
Cross the gear-box driving.
A kind of gas-turbine unit of technical solution 18. comprising:
Turbine, the turbine include turbine；
Compressor section, the compressor section are positioned at the upstream of the turbine, including low pressure compressor and height
Compressor is pressed, the high pressure compressor includes front part and rear portion；And
Gear-box, at least one of front part and rear portion of the high pressure compressor pass through institute by the turbine
State gear-box driving.
The gas-turbine unit according to technical solution 18 of technical solution 19., wherein the compressor it is described before
Portion part is driven by the turbine by the gear-box, so that the front part of the compressor is configured to than the pressure
The rear portion of contracting machine more slowly rotates.
The gas-turbine unit according to technical solution 18 of technical solution 20., further include:
Fan, wherein the fan is at least partly driven by the turbine by the gear-box.
With reference to the following description and the appended claims book, these and other features of the invention, aspect and advantage will become
It is best understood from.The Detailed description of the invention the embodiment of the present invention for being incorporated in this manual and forming part of this specification, and even
With the description together principle for explaining the present invention.
Detailed description of the invention
Illustrate complete and sufficient disclosure of the invention in the specification of reference attached drawing, including it is common for this field
Optimal mode for technical staff.
Fig. 1 provides the diagrammatic cross-sectional of the exemplary gas turbogenerator of the various exemplary embodiment according to this theme
Face view.
Fig. 2 provides the exemplary combustion of Fig. 1 including one or more gear-boxes of the exemplary embodiment according to this theme
The explanatory view of gas eddy turbine.
Fig. 3 is provided according to the exemplary embodiment of this theme with the rear section and axis being operatively coupled with gear-box
The schematic cross section of the separate compressor of the gas-turbine unit of streaming compressor.
Fig. 4 provide according to the exemplary embodiment of this theme with the centre portion being operatively coupled with gear-box and
The schematic cross section of the separate compressor of the gas-turbine unit of Axial Flow Compressor.
Fig. 5 is provided according to the exemplary embodiment of this theme with the front section and axis being operatively coupled with gear-box
Flow the schematic cross section of the separate compressor of the gas-turbine unit of compressor.
Fig. 6 is provided according to the exemplary embodiment of this theme with the rear centrifugation section being operatively coupled with gear-box
And the schematic cross section of the separate compressor of the gas-turbine unit of axial-centrifugal compressor.
Fig. 7 is provided according to the exemplary embodiment of this theme with the rear axial section being operatively coupled with gear-box
And the schematic cross section of the separate compressor of the gas-turbine unit of axial-centrifugal compressor.
Fig. 8 is provided according to the exemplary embodiment of this theme with the preceding axial section being operatively coupled with gear-box
And the schematic cross section of the separate compressor of the gas-turbine unit of axial-centrifugal compressor.
The reuse of appended drawing reference is intended to indicate same or similar feature or member of the invention in this specification and figure
Part.
Specific embodiment
With detailed reference to currently preferred embodiments of the present invention, one or more of examples are shown in the drawings.It retouches in detail
It states using number and alphabetical designation and refers to the feature in figure.It is referred in figure and in description using same or similar mark
Same or like part of the invention.As used herein, term " first ", " second " and " third " are used interchangeably to distinguish
One component and another component, and be not intended to indicate position or the importance of individual part.Term " upstream " and " downstream " are
Refer to the relative direction relative to the fluid flowing in fluid path.For example, " upstream " refers to the direction of fluid outflow, and
" downstream " refers to the direction of fluid flow direction.In addition, for example " about ", the approximate term of " substantially " or " about " refers to percent
In ten bouds on error.
The various aspects of the disclosure are related to a kind of gas-turbine unit with two speed separate compressor.Gas turbine hair
Motivation includes low pressure compressor, high pressure compressor, turbine and gear-box.High pressure compressor includes being divided into front part and posterior
The multiple grades divided.One or two of front part and rear portion of high pressure compressor are driven by turbine by gear-box,
Front part and rear portion are rotated at different rates.
Fig. 1 provides the schematic cross-section view of the gas-turbine unit of the exemplary embodiment according to present disclosure
Figure.More precisely, gas-turbine unit is high bypass turbofan jet engine 10, herein for the embodiment of Fig. 1
In be referred to as " fanjet 10 ".As shown in fig. 1, fanjet 10 defines that axial A (is parallel to offer for referring to
Longitudinal centre line 12 extend) and radial direction R.In general, turbofan 10 includes fan section 14 and is arranged under fan section 14
The core turbogenerator 16 of trip.
Discribed exemplary core turbogenerator 16 generally includes to limit the generally tube-like envelope of annular entry 20
Body 18.Outer housing 18 has been coated with serial flow relationship: compressor section comprising booster or low pressure (LP) compressor 22
With high pressure (HP) compressor 24；Burning block 26；Turbine comprising high pressure (HP) turbine 28 and low pressure (LP) turbine 30；
And jet exhaust nozzle segment 32.HP turbine 28 is drivingly connected to HP compressor 24 by high pressure (HP) axis or shaft 34.It is low
Press (LP) axis or shaft 36 that LP turbine 30 is drivingly connected to LP compressor 22.In the other embodiments of fanjet 10
In, it is possible to provide additional shaft, so that engine 10 can be described as multiple-rotor engine.
For discribed embodiment, fan section 14 includes variablepiston fan 38, and the variablepiston fan 38 has
There are the multiple fan blade 40 for being connected to disk 42 in a spaced apart manner.As depicted, fan blade 40 is substantially along diameter
Extend outwardly to R from disk 42.Each fan blade 40 can be rotated around pitch axis P relative to disk 42, the reason is that fan leaf
Piece 40 is operably linked to suitable actuating component 44, and the actuating component 44 is configured to jointly change fan leaf jointly
The pitch of piece 40.Fan blade 40, disk 42 and actuating component 44 can be by the LP axis 36 across power gear box 46 around vertical
It is rotated together to axis 12.Power gear box 46 includes multiple gears, for the rotation speed of LP axis 36 to be stepped down to
More efficient rotary fan speed.
Referring still to the exemplary embodiment of Fig. 1, disk 42 is covered by rotatable forward engine room 48, and forward engine room 48 is dynamic with air
Mechanics profile is to promote air-flow to pass through the multiple fan blade 40.In addition, exemplary fan section 14 includes ring-type fan shell
Body or external cabin 50, circumferentially surround at least part of fan 38 and/or core turbogenerator 16.It should be appreciated that
Cabin 50 may be configured to be supported relative to core turbogenerator 16 by multiple exit guide blades 52 being circumferentially spaced.This
Outside, the downstream section 54 of cabin 50 can extend on the outer portion of core turbogenerator 16, to define therebetween bypass gas
Circulation road 56.
During the operation of fanjet 10, large quantity of air 58 passes through the associated entry 60 and/or fan of cabin 50
Section 14 enters turbofan 10.When large quantity of air 58 crosses fan blade 40, first of the air 58 such as indicated by arrow 62
The second part for the air 58 for being guided or directing into bypass gas flow access 56, and such as indicated by arrow 64 is divided to be guided or lead
It guides in LP compressor 22.Ratio between the first part 62 of air and the second part 64 of air is commonly referred to as by-pass ratio.
When the second part 64 of air is guided through high pressure (HP) compressor 24 and enters burning block 26, the second part of air
64 pressure then increases, and at burning block 26, air and fuel mix combining combustion to provide burning gases 66.
Burning gases 66 are guided through HP turbine 28, fixed via the HP turbine for being connected to outer housing 18 at HP turbine 28
The order levels of sub- wheel blade 68 and the HP turbine rotor blade 70 for being connected to HP axis or shaft 34 extract the heat from burning gases 66
A part of energy and/or kinetic energy, therefore rotate HP axis or shaft 34, and then support the operation of HP compressor 24.Burning gases
66 are then guided through LP turbine 30, via the LP turbine stator wheel blade 72 for being connected to outer housing 18 and even at LP turbine 30
The order levels for being connected to the LP turbine rotor blade 74 of LP axis or shaft 36 extract the of thermal energy from burning gases 66 and kinetic energy
Two parts, therefore rotate LP axis or shaft 36, and then support the operation of LP compressor 22 and/or the rotation of fan 38.
Burning gases 66 are then guided through the jet exhaust nozzle segment 32 of core turbogenerator 16 and are pushed away with providing
Into power.Meanwhile when the first part of air 62 is guided through before the discharge of the fan nozzle exhaust section 76 of turbofan 10
When bypass gas flow channel 56, the pressure of the first part 62 of air is significantly increased, to also provide propulsive force.HP turbine 28, LP
Turbine 30 and jet exhaust nozzle segment 32 at least partially define hot gas path 78, with logical for guiding burning gases 66
Cross core turbogenerator 16.
It will be appreciated, however, that exemplary fanjet 10 is only depicted in Fig. 1 by way of example, and in other examples
In property embodiment, fanjet 10 can have any other suitable configuration, this theme is applicable to other kinds of whirlpool
Turbine.For example, in other exemplary embodiments of the invention, fanjet 10 is alternatively configured to for example directly drive whirlpool
Fan engine, fixedpiston fanjet etc..Additionally or alternatively property, fanjet 10 may be configured to turbine spiral shell
Revolve paddle motor, turbojet engine, turboshaft engine, punching engine, auxiliary power unit engine etc..Additionally or alternatively
Property, in other embodiments, the fanjet 10 of Fig. 1, which is alternatively configured to navigate, changes gas-turbine unit, such as with
In marine use, or it is configured to industrial gas turbine engine, such as generating electricity.
Referring now to Fig. 2, the combustion gas including one or more gear-boxes of the exemplary embodiment according to this theme is provided
The schematic diagram of turbogenerator.More specifically, Fig. 2 provides the schematic diagram of fanjet 10, similar attached drawing mark is used
Note is to refer to identical component.It will be appreciated, however, that fanjet 10 is used only as exemplary engine, to describe this master
The many aspects of topic.Can retrofit fanjet 10, and these remodeling can be in the range of this theme.In addition, turbofan
Engine 10 can be configured for other application, such as other gas-turbine units or any other suitable application, wherein
Wish each grade of speed of the compressor of change gas-turbine unit.
As shown in Figure 2 and as described above, fanjet 10 generally includes the fan 38 arranged with crossfire sequence, pressure
Contracting machine section 102, burning block 26 and turbine 104.More specifically, according to illustrated embodiment, compressor section 102 includes
It is positioned at the LP compressor 22 of the upstream of HP compressor 24, turbine 104 includes the whirlpool HP for being positioned at the upstream of LP turbine 30
Wheel 28.It will be appreciated that though compressor section 102 and turbine 104 are respectively depicted as tool herein, there are two compressors
And turbine, but alternate embodiments may include having any appropriate number of compressor and the whirlpool of any appropriate number of grade
Wheel.
As described above, it is often desirable that operate in LP compressor 22 and HP compressor 24 or these compressors at different rates
Grade.Therefore, according to the exemplary embodiment of this theme, fanjet 10 includes one or more gear-boxes 110, gear-box
110 are configured so that different rotary parts can at different rates or direction rotates, to reduce entire engine size simultaneously
Improve entire engine performance and efficiency.As used herein, " grade " of compressor or turbine is intended to indicate that a pair of of rotation and consolidates
Determine aerofoil profile.The speed of specific grade refers to the rotation speed of rotating airfoils.It should be understood that each compressor is by multiple stackings
Grade composition, these grades make air be transmitted to burning block 26 with the air that gradually reduces before being burnt.
As shown in Fig. 2, HP compressor 24 includes front part 112 and rear portion 114.More specifically, front part 112
It may include one or more compressor stages, rear portion may include one or more compressor stages.Accoding to exemplary embodiment, preceding
One or two of portion part 112 and rear portion 114 are operably linked to turbine 104 by gear-box 110.This
Sample, for example, at least one of the front part 112 and rear portion 114 of HP compressor 24 pass through gear-box by HP turbine 28
110 drivings.
More specifically, the front part 112 of HP compressor 24 passes through gear-box by HP turbine 28 according to illustrated embodiment
110 drivings, so that the front part 112 of HP compressor 24 is configured to more slowly rotate than the rear portion 114 of HP compressor 24.
In this way, HP compressor 24 is segmented into two different sections, gear-box 110 allows each section to rotate at different rates.
In this way, rear portion 114 can be operated with higher speed to increase the pressure ratio ability of HP compressor 24, and front part
112 can be operated with lower speed to keep the tip speed of front part 112 in the desired range.
As it is used herein, gear-box 110 can refer to any dress for being suitable for transmitting mechanical force between rotary part
It sets or multiple devices.Accoding to exemplary embodiment, gear-box 110 is the epicyclic gearbox with planetary gear train or construction.So
And according to alternate embodiments, gear-box 110 may include any suitable combination or planetary gear, helical gear, spur gear, snail
Wheel, bevel gear are used for any other mechanically operated suitable component.
According to the alternate embodiments of this theme, gear-box 110 can also be operably linked to the wind of fan section 14
Fan 38.In this way, fan 38 is at least partly driven by LP turbine 30 by gear-box 110 by turbine 104 or more specifically.
It is worth noting that, when gear-box 110 is used for driving fan 38, as shown in the dotted line gear-box 110 in Fig. 2, gear-box 110
It can be operated together with power gear box 46, or power gear box 46 can be fully phased out.
In fact, gear-box 110 can be configured to operationally join turbine 104 (HP turbine 28 or LP turbine 30)
It is connected to any desired part of fanjet 10.For example, LP compressor 22 can also pass through gear-box by turbine 104
110 drivings.In addition, gear-box 110 can be connected to front part 112 and rear portion 114, for example, making HP turbine 28 can
With different rotation speeds and with the speed operation front part 112 different from the rotation speed of HP turbine 28 and posterior
Divide 114.
Other than part in addition to making compressor section 102 rotates at different rates, accoding to exemplary embodiment, gear-box
110 may be configured for rotating part in a different direction.For example, front part 112 constructs according to one embodiment
It is rotated at along the first circumferencial direction, rear portion 114 is configured to rotate along the second circumferencial direction.According to one embodiment, first
Circumferencial direction is identical as the second circumferencial direction, and in another embodiment, it is opposite.According to other embodiments, gear
Case 110 can be connected to LP compressor 22 and HP compressor, in different directions and/or friction speed drives these compressors
Or the grade of these compressors.
Referring now to Fig. 3 to 8, the signal of the viewgraph of cross-section and turbine 104 of gas-turbine unit is shown
One or more parts of figure, compressor section 102 are coupled by exemplary gearbox 110.More specifically, Fig. 3 to 5 shows axis
Streaming engine 120, the combustor section 26 with axial orientation (similar to the fanjet 10 in Fig. 1).Compared to it
Under, Fig. 6 to 8 shows axial-flow engine 122, has the centrifugation for leading to combustor section 26 or radial entrance.It is identical
Appended drawing reference will be used to indicate and the same or similar component in this two group picture.
As shown in Fig. 3 to 8, the front part 112 of HP compressor 24 includes limit the first average axial spacing 132 first
Multi-stage compression rotor blade 130.Similarly, the rear portion 114 of HP compressor 24 includes limiting the second average axial spacing
136 the second multi-stage compression rotor blade 134.As used herein, " average axial spacing ", when for referring to particular compressor
When grade, axially A (Fig. 1) can be in the downstream edge 140 and adjacent downstream rotor blade of upstream rotor blade 142
The average distance measured between 146 upstream edge 144.According to one embodiment, the second average axial spacing 136 is less than or waits
In twice of the first average axial spacing 132.According to another embodiment, the second average axial spacing 136 is less than or equal to the
One average axial spacing 132.
In addition, accoding to exemplary embodiment, the first average axial spacing 132 and the second average axial spacing 136 can be with
Rotor blade it is at different levels highly relevant.In this respect, for example, the first average axial spacing 132 can be the first multi-stage compression
Between about the 10% and 30% of the mean leaf height of rotor blade 130, or about 20%.Similarly, for example, second is flat
Equal axial spacing 136 can be the mean leaf height of the second multi-stage compression rotor blade 134 about 40% and 60% it
Between, or about 50%.
According to the exemplary embodiment of this theme, gear-box 110 can be positioned on any suitable in gas-turbine unit
Position.For example, with reference to Fig. 3 and 6, gear-box 110 is with 114 aligned adjacent of rear portion of HP compressor 24 or downstream.Root
According to another embodiment, compressor section 26 further includes compressor discharge nozzle module 150 comprising for entering combustion zone
The diffuser 152 of compressed air is spread before section 26.Accoding to exemplary embodiment, the installation of gear-box 110 to compressor discharge sprays
Mouth module 150.
Alternatively, as illustrated in figures 4 and 7, gear-box 110 can be axially positioned on middle position along HP compressor 24.So
Positioning, gear-box 110 can be operably linked to the rear portion of the front part 112 of HP compressor 24, HP compressor
114, any other of the middle section of HP compressor 24 or the rotor blades at different levels in HP compressor 24 suitably combine.It can
Alternatively, as shown in figs. 5 and 8, gear-box 110 be aligned with the front part 112 of HP compressor 24 or even with HP compressor 24
More front alignment.According to further embodiment, gear-box 110 can be positioned on HP compressor 24 or LP compressor 22 upstream and
Any position in the downstream of fan 38.
Although wherein HP compressor 24 is divided into front part 112 with after Fig. 2 shows LP compressor 22 and HP compressor 24
Portion part 114, it should be understood that this configuration of fanjet 10 is merely exemplary and is not intended to be limiting this theme
Range.For example, LP compressor 22 and/or HP compressor 24 are segmented into any appropriate number of grade, and each corresponding stage
It can need to be operably linked to gear-box 110 according to specific application.Further, it is possible to use have any suitable dimension or
The more than one gear-box 110 for being used to drive each grade of configuration.
In addition, although all embodiments shown in this article all have the tooth for the one or more grades for being connected to HP compressor 24
Roller box 110, but it is to be understood that this configuration is merely exemplary, it is no intended to limit the range of this theme.For example, gear
Case 110 can be operatively coupled any two rotary part in the core turbogenerator 16 of fanjet 10, so as to
The rotation speed of slave unit is reduced or increased.
The foregoing describe the gas-turbine units with two speed separate compressor.More specifically, for example, gas turbine
The high pressure compressor of engine is divided into two different sections, and wherein gear-box allows each section to revolve at different rates
Turn.The high-pressure turbine of driving compressor can be directly coupled to one of compressor section or gear is attached to the two, allow most
More three kinds of different revolving speeds.Two sections of compressor can be axial stream and axial stream, axial stream and centrifugation stream or centrifugation and
Centrifugation stream.The accurate series of any axial section can be customized for specific application and aerodynamic design.Gear-box
Itself can be located at the front of two compressor sections, the rear portion of two compressor sections or be located at two compressor sections it
Between line of demarcation at.The other configurations of gas-turbine unit are possible and it is contemplated that in the range of this themes.
It is worth noting that, it is preferably fixed that theme as described herein can be used by the way that compressor is divided into two sections
Make the rotation speed of each section.In this way, the overall performance and pressure ratio ability of the compression stage of given quantity can be improved.Separately
Outside, the speed for increasing the rear ministerial level of compressor can reduce its physical size.Therefore, can make to fire using the various aspects of this theme
Gas eddy turbine has improved overall dimensions, efficiency and fuels combustion capability.
This written description uses examples to disclose the present invention, including best mode, and also makes the technology people of fields
Member can implement the present invention, including manufacturing and using any device or system and executing any method being incorporated to.Of the invention
Patentable scope is defined by the claims, and may include other examples that those skilled in the art expects.If
Such other examples include having no different structural details from the literal language of claims, or if it includes wanting with right
Ask the literal language of book without the equivalent structural elements of essence difference, then it is contemplated that range of such other examples in claims
It is interior.
Claims (10)
1. a kind of gas-turbine unit comprising:
Turbine, the turbine include turbine；
Compressor section, the compressor section are positioned at the upstream of the turbine and including compressor, the compressions
Machine includes front part and rear portion；And
Gear-box, at least one of front part and rear portion of the compressor pass through the gear-box by the turbine
Driving.
2. gas-turbine unit according to claim 1, wherein the front part of the compressor includes first
Multi-stage compression rotor blade, the first multi-stage compression rotor blade limit the first average axial spacing, and wherein, institute
The rear portion for stating compressor includes the second multi-stage compression rotor blade, and the second multi-stage compression rotor blade limits the
Two average axial spacings, and wherein, the described second average axial spacing is less than or equal to the described first average axial spacing
Twice.
3. gas-turbine unit according to claim 2, wherein the described second average axial spacing is less than or equal to institute
State the first average axial spacing.
4. gas-turbine unit according to claim 1, wherein the front part of the compressor is by the whirlpool
Wheel is driven by the gear-box, so that the front part of the compressor is configured to the rear portion than the compressor
Part more slowly rotates.
5. gas-turbine unit according to claim 1, wherein the front part of the compressor and it is described after
Portion part is driven by the turbine by the gear-box.
6. gas-turbine unit according to claim 1, wherein the compressor section further includes compressor discharge spray
Mouth module, wherein the gear-box is installed to the compressor discharge nozzle module.
7. gas-turbine unit according to claim 1, wherein the gear-box is along the gas-turbine unit
Axial direction be aligned with the rear portion of the front part of the compressor or the compressor.
8. gas-turbine unit according to claim 1, further include:
Fan, wherein the fan is at least partly driven by the turbine by the gear-box.
9. gas-turbine unit according to claim 1, wherein the compressor is high pressure compressor, wherein described
Compressor section further includes low pressure compressor, and wherein, and the low pressure compressor is driven by the turbine by the gear-box
It is dynamic.
10. a kind of gas-turbine unit comprising:
Turbine, the turbine include turbine；
Compressor section, the compressor section are positioned at the upstream of the turbine, including low pressure compressor and high pressure pressure
Contracting machine, the high pressure compressor include front part and rear portion；And
Gear-box, at least one of front part and rear portion of the high pressure compressor pass through the tooth by the turbine
Roller box driving.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US15/795,380 US10677159B2 (en) | 2017-10-27 | 2017-10-27 | Gas turbine engine including a dual-speed split compressor |
| US15/795,380 | 2017-10-27 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109723559A true CN109723559A (en) | 2019-05-07 |
| CN109723559B CN109723559B (en) | 2022-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811255881.6A Active CN109723559B (en) | 2017-10-27 | 2018-10-26 | Gas turbine engine including two-speed split compressor |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US10677159B2 (en) |
| CN (1) | CN109723559B (en) |
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| US11174916B2 (en) | 2019-03-21 | 2021-11-16 | Pratt & Whitney Canada Corp. | Aircraft engine reduction gearbox |
| US11268453B1 (en) | 2021-03-17 | 2022-03-08 | Pratt & Whitney Canada Corp. | Lubrication system for aircraft engine reduction gearbox |
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| GB201903261D0 (en) | 2019-03-11 | 2019-04-24 | Rolls Royce Plc | Efficient gas turbine engine installation and operation |
| GB201903262D0 (en) | 2019-03-11 | 2019-04-24 | Rolls Royce Plc | Efficient gas turbine engine installation and operation |
| GB201903257D0 (en) | 2019-03-11 | 2019-04-24 | Rolls Royce Plc | Efficient gas turbine engine installation and operation |
| US11136899B2 (en) | 2019-06-14 | 2021-10-05 | Raytheon Technologies Corporation | Integrated electro-aero-thermal turbine engine |
| US11319882B2 (en) | 2019-09-10 | 2022-05-03 | Raytheon Technologies Corporation | Gear and electric amplification of generator motor compressor and turbine drives |
| WO2022085024A1 (en) * | 2020-10-22 | 2022-04-28 | Indian Institute Of Technology, Kharagpur | Axial-centrifugal contra-rotating light weight, compact compression system. |
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Also Published As
| Publication number | Publication date |
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| US10677159B2 (en) | 2020-06-09 |
| US20190128181A1 (en) | 2019-05-02 |
| CN109723559B (en) | 2022-01-04 |
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